[Federal Register: April 14, 2008 (Volume 73, Number 72)]
[Rules and Regulations]
[Page 19971-19972]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ap08-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25173; Directorate Identifier 2006-NE-24-AD;
Amendment 39-15453; AD 2008-08-01]
RIN 2120-AA64
Airworthiness Directives; McCauley Propeller Systems Propeller
Models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/
114HCA-0, and C5JFR36C1104/L114HCA-0
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding three existing airworthiness directives
(ADs) for McCauley Propeller Systems propeller models B5JFR36C1101/
114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and
C5JFR36C1104/L114HCA-0. Those ADs currently require fluorescent
penetrant inspections (FPI) and eddy current inspections (ECI) of
propeller blades for cracks, and if any crack indications are found,
removing the blade from service. This AD requires the same initial
inspections, but extends the compliance times and intervals, adds
repetitive inspections, and mandates a life limit for the blades. This
AD results from our determination that we must require repetitive
inspections for cracks, and from reports of blunt leading edges of the
propeller blades due to erosion. We are issuing this AD to detect
cracks in the propeller blade that could cause failure and separation
of the propeller blade and loss of control of the airplane, and to
detect blunt leading edges on the propeller blades, which could cause
airplane single engine climb performance degradation and could result
in an increased risk of collision with terrain.
DATES: This AD becomes effective May 19, 2008. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of May 19, 2008.
ADDRESSES: You can get the service information identified in this AD
from McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277-7704,
telephone (800) 621-7767.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, Small Airplane Directorate,
1801 Airport Road, Room 100, Wichita, KS 67209; e-mail:
jeff.janusz@faa.gov; telephone: (316) 946-4148; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2003-15-01, Amendment 39-13243 (68 FR 42244, July 17,
2003); AD 2003-17-10, Amendment 39-13285 (68 FR 50462, August 21,
2003); and AD 2006-15-13, Amendment 39-14693 (71 FR 42258, July 26,
2006), with a proposed AD. The proposed AD applies to McCauley
Propeller Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/
L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0. We
published the proposed AD in the Federal Register on November 1, 2007
(72 FR 61824). That action proposed to require the same initial
inspections as the three ADs being superseded, but to extend the
compliance times and intervals, to add repetitive inspections, and to
mandate a life limit for the blades.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the one comment received.
The commenter supports the proposal. We also found we needed to clarify
that blades that had crack indications were no longer eligible for
installation on any other airframe or in any other configuration. We
clarified the AD on the point.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD will affect 22 propeller assemblies
installed on airplanes of U.S. registry. We estimate that it will take
about 47 work-hours per propeller to perform the required actions, and
that the average labor rate is $80 per work-hour. Required parts will
cost about $260 per propeller. Based on these figures, we estimate the
total cost of the AD to U.S. operators to be $88,440.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in
[[Page 19972]]
the AD Docket. You may get a copy of this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13243 (68 FR
42244, July 17, 2003), Amendment 39-13285 (68 FR 50462, August 21,
2003), and Amendment 39-14693 (71 FR 42258, July 26, 2006), and by
adding a new airworthiness directive, Amendment 39-15453, to read as
follows:
2008-08-01 McCauley Propeller Systems: Amendment 39-15453. Docket
No. FAA-2006-25173; Directorate Identifier 2006-NE-24-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 19,
2008.
Affected ADs
(b) This AD supersedes AD 2003-15-01, Amendment 39-13243; AD
2003-17-10, Amendment 39-13285; and AD 2006-15-13, Amendment 39-
14693.
Applicability
(c) This AD applies to McCauley Propeller Systems propeller
models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/
114HCA-0, and C5JFR36C1104/L114HCA-0. These propellers are installed
on BAE Systems (Operations) Limited Jetstream Model 4100 and 4101
series airplanes (Jetstream 41).
Unsafe Condition
(d) This AD results from our determination that we must require
repetitive inspections for cracks, and from reports of blunt leading
edges of the propeller blades due to erosion. We are issuing this AD
to detect cracks in the propeller blade that could cause failure and
separation of the propeller blade and loss of control of the
airplane, and to detect blunt leading edges on the propeller blades,
which could cause airplane single engine climb performance
degradation and could result in an increased risk of collision with
terrain.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Life Limit
(f) Remove all 114GCA-0, L114GCA-0, 114HCA-0, and L114HCA-0
propeller blades upon reaching 10,000 operating hours time-since-
new.
Initial Propeller Blade Inspection
(g) Perform an initial fluorescent penetrant inspection and eddy
current inspection of propeller blades. Use the Equipment Required
and Accomplishment Instructions of McCauley Propellers Alert Service
Bulletin ASB255, dated January 8, 2007, and the following compliance
schedule:
Table 1.--Compliance Schedule
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Then inspect the propeller
If the propeller blade: blade:
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(1) Has more than 2,400 operating hours Within 100 operating hours time-
time-since-new (TSN), time-since-last in-service (TIS) after the
inspection (TSLI), or time-since- effective date of this AD.
overhaul (TSO).
(2) Has 2,400 or fewer operating hours Upon reaching 2,500 operating
TSN, TSLI, or TSO. hours TSN, TSLI, or TSO.
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Propeller Blades Found Cracked
(h) Remove from service propeller blades found with any crack
indications. Blades found with crack indications are no longer
eligible for installation in any configuration. Do not install them
in any configuration on any airframe.
Repetitive Propeller Blade Inspection
(i) Thereafter, inspect the propeller blades within 2,500
operating hours TSLI or TSO. Use the Equipment Required and
Accomplishment Instructions of McCauley Propellers Alert Service
Bulletin ASB255, dated January 8, 2007.
Inspection for Blunt Erosion on the Leading Edge of the Propeller Blade
(j) Every time the propeller is removed for the inspection for
cracks, inspect the blade for erosion and, if necessary, repair the
erosion. The McCauley Propeller Systems Blade Overhaul Manual No.,
BOM 100, contains information on inspecting and repairing erosion on
the propeller blade.
Reporting Requirements
(k) Within 10 calendar days of the inspection, use the Reporting
Form for Service Bulletin 255 to report all inspection findings to
McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277-7704,
telephone (800) 621-7767.
(l) The Office of Management and Budget (OMB) has approved the
reporting requirements and assigned OMB control number 2120-0056.
Alternative Methods of Compliance
(m) The Manager, Wichita Aircraft Certification Office, has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Special Flight Permits
(n) Under 39.23, we are limiting the availability of special
flight permits for this AD. Special flight permits are available
only if:
(1) The operator has not seen signs of external oil leakage from
the hub; and
(2) The operator has not observed abnormal propeller vibration
or abnormal engine vibration; and
(3) The operator has not observed any other abnormal operation
from the propeller; and
(4) The operator has not made earlier reports of abnormal
propeller vibration, abnormal engine vibration, or other abnormal
propeller operations that have not been addressed.
Related Information
(o) Contact Jeff Janusz, Aerospace Engineer, Wichita Aircraft
Certification Office, FAA, Small Airplane Directorate, 1801 Airport
Road, Room 100, Wichita, KS 67209; e-mail: jeff.janusz@faa.gov;
telephone: (316) 946-4148; fax: (316) 946-4107, for more information
about this AD.
Material Incorporated by Reference
(p) You must use the McCauley Propellers Alert Service Bulletin
ASB255, dated January 8, 2007, to perform the inspections required
by this AD. The Director of the Federal Register approved the
incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. Contact McCauley Propeller
Systems, P.O. Box 7704, Wichita, KS 67277-7704, telephone (800) 621-
7767, for a copy of this service information. You may review copies
at the FAA, New England Region, 12 New England Executive Park,
Burlington, MA; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on March 31, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-7162 Filed 4-11-08; 8:45 am]
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